U.S. patent number 6,244,542 [Application Number 09/357,595] was granted by the patent office on 2001-06-12 for rotor driven edge.
This patent grant is currently assigned to Northrop Grumman Corporation. Invention is credited to Steven Louis Pauletti, Kendall Gardner Young.
United States Patent |
6,244,542 |
Young , et al. |
June 12, 2001 |
Rotor driven edge
Abstract
In accordance with the present invention, there is provided an
aerodynamic control device for use with an aerodynamic lifting
member. The lifting member is defined by a horizontal reference
plane disposed therethrough. The control device is provided with at
least one support rotor extending from the lifting member. The
support rotor is sized and configured to rotate about a rotor axis
of rotation which is disposed generally parallel to the horizontal
reference plane. The support rotor has an inboard segment which is
disposed along the rotor axis of rotation and in rotational
communication with the lifting member. The support rotor has an
outboard segment disposed off-set from the rotor axis of rotation.
The control device is further provided with a control device body
which is engaged with the outboard segment of the support rotor.
The control device body is sized and configured to translate
generally orthogonal to the horizontal reference plane in response
to rotation of the support rotor.
Inventors: |
Young; Kendall Gardner
(Coppell, TX), Pauletti; Steven Louis (Mesquite, TX) |
Assignee: |
Northrop Grumman Corporation
(Los Angeles, CA)
|
Family
ID: |
23406265 |
Appl.
No.: |
09/357,595 |
Filed: |
July 20, 1999 |
Current U.S.
Class: |
244/213;
244/225 |
Current CPC
Class: |
B64C
9/16 (20130101); B64C 9/02 (20130101); B64C
3/50 (20130101) |
Current International
Class: |
B64C
9/02 (20060101); B64C 9/16 (20060101); B64C
3/00 (20060101); B64C 7/00 (20060101); B64C
3/50 (20060101); B64C 9/00 (20060101); B64C
009/00 () |
Field of
Search: |
;244/211-215,219,225,9R |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Poon; Peter M.
Assistant Examiner: Jakel; Kevin
Attorney, Agent or Firm: Anderson; Terry J. Hoch, Jr.; Karl
J.
Claims
What is claimed is:
1. An aerodynamic control device for use with an aerodynamic
lifting member, the lifting member being defined by a horizontal
reference plane disposed therethrough, the control device
comprising:
at least one support rotor extending from the lifting member, the
support rotor being sized and configured to rotate about a rotor
axis of rotation disposed generally parallel to the horizontal
reference plane, the support rotor having an inboard segment
disposed along the rotor axis of rotation and in rotational
communication with the lifting member, the support rotor having an
outboard segment disposed off-set from the rotor axis of rotation,
the inboard and outboard segments of the support rotor being
aligned generally parallel to each other; and
a control device body engaged with the outboard segment of the
support rotor, the control device body being sized and configured
to translate generally orthogonal to the horizontal reference plane
in response to rotation of the support rotor.
2. The aerodynamic control device of claim 1 wherein the outboard
segment of the support rotor is in rotational engagement with the
control device body.
3. The aerodynamic control device of claim 1 wherein the outboard
segment of the support rotor is in slidable engagement with the
control device body.
4. The aerodynamic control device of claim 3 wherein the control
device body having a slot formed therein, the outboard segment of
the support rotor is sized and configured to slidably engage the
slot.
5. The aerodynamic control device of claim 1 wherein the at least
one support rotor comprises a pair of support rotors.
6. The aerodynamic control device of claim 5 wherein the support
rotors are sized and configured to rotate in opposing rotational
directions for translating the control device body orthogonal to
the horizontal reference plane.
7. The aerodynamic control device of claim 1 wherein the control
device body has a trailing edge.
8. The aerodynamic control device of claim 7 wherein the rotor axis
of rotation is disposed generally perpendicular to the trailing
edge of the control device body.
9. The aerodynamic control device of claim 1 further comprises a
rotational actuator for rotating the support rotor, the actuator
being disposable within the lifting member and in mechanical
communication with the inboard segment of the support rotor.
10. The aerodynamic control device of claim 1 further comprises a
flexible outer skin attached to the lifting member and the control
device body, the outer skin is sized and configured to deform in
response to translation of the control device body.
11. The aerodynamic control device of claim 10 wherein the flexible
outer skin is formed of an elastomeric material.
12. The aerodynamic control device of claim 1 wherein the lifting
member has upper and lower lifting member surfaces and the control
device body has upper and lower body surfaces, the control device
further comprises upper and lower flexible outer skins, the upper
flexible outer skin is attached to the upper lifting member surface
and the upper body surface, the lower flexible outer skin is
attached to the lower lifting member surface and the lower body
surface.
13. The aerodynamic control device of claim 12 wherein the control
device body has an upper deflected position with the control device
body translated in a direction of the upper body surface and the
upper and lower flexible outer skins being disposed in tension.
14. The aerodynamic control device of claim 12 wherein the control
device body has a lower deflected position with the control device
body translated in a direction of the lower body surface and the
upper and lower flexible outer skins being disposed in tension.
15. The aerodynamic control device of claim 1 wherein the control
device body has opposing first and second ends thereof, the control
device further comprises first and second transition portions
respectively attached to the first and second ends of the control
device body, the first and second transition portions are attached
to the lifting member.
16. The aerodynamic control device of claim 15 wherein the first
and second transition portions are sized and configured to deform
in response to translation of the control device body.
17. The aerodynamic control device of claim 16 wherein the first
and second transition portions are sized and configured to deform
into an S-shape.
18. The aerodynamic control device of claim 15 wherein the
aerodynamic lifting member has an indenture formed therein, the
indenture being defined by first and second shoulder portions, the
first and second transition portions are respectively attached to
the first and second shoulder portions.
19. The aerodynamic control device of claim 15 further comprises a
flexible outer skin attached to the lifting member, the control
device body and the first and second transition portions, the outer
skin is sized and configured to deform in response to translation
of the control device body.
20. The aerodynamic control device of claim 15 wherein the lifting
member has upper and lower lifting member surfaces, the control
device body has upper and lower body surfaces, the first and second
transition portions respectively have upper and lower surfaces
thereof, the control device further comprises upper and lower
flexible outer skins, the upper flexible outer skin is attached to
the upper lifting member surface, the upper body surface and the
upper surfaces of the first and second transition portions, the
lower flexible outer skin is attached to the lower lifting member
surface, the lower body surface and the lower surfaces of the first
and second transition portions.
21. The aerodynamic control device of claim 20 wherein the control
device body has an upper deflected position with the control device
body translated in a direction of the upper body surface and the
upper and lower flexible outer skins being disposed in tension.
22. The aerodynamic control device of claim 20 wherein the control
device body has a lower deflected position with the control device
body translated in a direction of the lower body surface and the
upper and lower flexible outer skins being disposed in tension.
23. An aerodynamic lifting member being generally defined by a
horizontal reference plane disposed therethrough, the lifting
member comprising:
a lifting member body having an indenture formed therein, the
indenture being defined by first and second shoulder portions;
and
a control device attached to the lifting member body, the control
device having first and second transition portions, the first and
second transition portions being respectively attached to the first
and second shoulder portions of the lifting member body, the
control device comprising:
at least one support rotor extending from the lifting member body,
the support rotor being sized and configured to rotate about a
rotor axis of rotation disposed generally parallel to the
horizontal reference plane, the support rotor having an inboard
segment disposed along the rotor axis of rotation and in rotational
communication with the lifting member body, the support rotor
having an outboard segment disposed off-set from the rotor axis of
rotation; and
a control device body having opposing first and second ends, the
first and second ends being respectively attached to the first and
second transition portions of the control device, the control
device body being engaged with the outboard segment of the support
rotor, the control device body being sized and configured to
translate generally orthogonal to the horizontal reference plane in
response to rotation of the support rotor.
24. The aerodynamic lifting member of claim 23 wherein the lifting
member body is a wing.
25. An aerodynamic control device for use with an aerodynamic
lifting member, the lifting member having upper and lower lifting
member surfaces, the lifting member being defined by a horizontal
reference plane disposed therethrough, the control device
comprising:
at least one support rotor extending from the lifting member, the
support rotor being sized and configured to rotate about a rotor
axis of rotation disposed generally parallel to the horizontal
reference plane, the support rotor having an inboard segment
disposed along the rotor axis of rotation and in rotational
communication with the lifting member, the support rotor having an
outboard segment disposed off-set from the rotor axis of
rotation;
upper and lower flexible outer skins; and
a control device body having upper and lower body surfaces, the
upper flexible outer skin being attached to the upper lifting
member surface and the upper body surface, the lower flexible outer
skin being attached to the lower lifting member surface and the
lower body surface, the control device body having an upper
deflected position with the control device body translated in a
direction of the upper body surface and the upper and lower
flexible outer skins being disposed in tension, the control device
body being engaged with the outboard segment of the support rotor,
the control device body being sized and configured to translate
generally orthogonal to the horizontal reference plane in response
to rotation of the support rotor.
26. The aerodynamic control device of claim 25 wherein the control
device body has a lower deflected position with the control device
body translated in a direction of the lower body surface and the
upper and lower flexible outer skins being disposed in tension.
27. An aerodynamic control device for use with an aerodynamic
lifting member, the lifting member having an indenture formed
therein, the indenture being defined by first and second shoulder
portions, the lifting member being defined by a horizontal
reference plane disposed therethrough, the control device
comprising:
at least one support rotor extending from the lifting member, the
support rotor being sized and configured to rotate about a rotor
axis of rotation disposed generally parallel to the horizontal
reference plane, the support rotor having an inboard segment
disposed along the rotor axis of rotation and in rotational
communication with the lifting member, the support rotor having an
outboard segment disposed off-set from the rotor axis of
rotation;
first and second transition portions, the first and second
transition portions being respectively attached to the first and
second shoulder portions; and
a control device body having opposing first and second ends, the
first and second ends being respectively attached to the first and
second transition portions of the control device, the control
device body being engaged with the outboard segment of the support
rotor, the control device body being sized and configured to
translate generally orthogonal to the horizontal reference plane in
response to rotation of the support rotor.
28. The aerodynamic control device of claim 27 wherein the first
and second transition portions are sized and configured to deform
in response to translation of the control device body.
29. The aerodynamic control device of claim 28 wherein the first
and second transition portions are sized and configured to deform
into an S-shape.
30. The aerodynamic control device of claim 27 further comprises a
flexible outer skin attached to the lifting member, the control
device body and the first and second transition portions, the outer
skin being sized and configured to deform in response to
translation of the control device body.
31. An aerodynamic control device for use with an aerodynamic
lifting member, the lifting member having upper and lower lifting
member surfaces, the lifting member being defined by a horizontal
reference plane disposed therethrough, the control device
comprising:
at least one support rotor extending from the lifting member, the
support rotor being sized and configured to rotate about a rotor
axis of rotation disposed generally parallel to the horizontal
reference plane, the support rotor having an inboard segment
disposed along the rotor axis of rotation and in rotational
communication with the lifting member, the support rotor having an
outboard segment disposed off-set from the rotor axis of
rotation;
upper and lower flexible outer skins;
first and second transition portions respectively having upper and
lower surfaces, the first and second transition portions being
attached to the lifting member; and
a control device body having upper and lower body surfaces, the
control device body further having opposing first and second ends,
the first and second ends being respectively attached to the first
and second transition portions of the control device, the upper
flexible outer skin being attached to the upper lifting member
surface, the upper body surface and the upper surfaces of the first
and second transition portions, the lower flexible outer skin being
attached to the lower lifting member surface, the lower body
surface and the lower surfaces of the first and second transition
portions, the control device body having an upper deflected
position with the control device body translated in a direction of
the upper body surface and the upper and lower flexible outer skins
being disposed in tension, the control device body being engaged
with the outboard segment of the support rotor, the control device
body being sized and configured to translate generally orthogonal
to the horizontal reference plane in response to rotation of the
support rotor.
32. The aerodynamic control device of claim 31 wherein the control
device body has a lower deflected position with the control device
body translated in a direction of the lower body surface and the
upper and lower flexible outer skins being disposed in tension.
Description
FIELD OF THE INVENTION
The present invention relates generally to aircraft aerodynamic
control surfaces, and more particularly to an aerodynamic control
device configured to vertically translate.
BACKGROUND OF THE INVENTION
Conventional fixed winged aircraft are provided with a variety of
aerodynamic control devices which include, for example, flaps,
elevators, ailerons, trim tabs, and rudders. These control devices
cooperatively operate to increase or decease lift over a given
localized aerodynamic control surface for achieving pitch, yaw and
roll control of the aircraft. Such control devices are used in both
traditional winged and modern stealthy aircraft designs.
These control devices are typically rigid structures which are
integrated into the edges of the wings or body (i.e., aerodynamic
lifting surfaces) of the aircraft. The control devices are
configured to deflect or rotate about an axis of rotation in a
hinge-like fashion with respect to the attached aerodynamic lifting
surfaces. Traditionally, these conventional control devices are
actuated by the application of torque about an axis which is
parallel to the trailing edge of the device. As such, the torque or
power requirement of such devices is directly proportional to
impinging air loads as the control device is rotated into an
oncoming airflow. Thus, the greater the desired control device
deflection, the greater the torque required to cause and maintain
such deflection.
In addition, these conventional control devices are generally rigid
structures which maintain their shape while being deflected or
rotated about an axis which is generally parallel to the wing
trailing edge. As such, gaps or abrupt contour changes occur at the
lateral hinge line area of these conventional control devices.
Further, as the control devices are rotated, chordwise gaps are
formed between the edges of the hinged control devices and the
adjacent fixed portions of the wing assembly.
It is contemplated that gaps, abrupt changes, or contour
discontinuities occurring between the aerodynamic lifting surface
and the attached control device are especially undesirable because
they tend to increase aerodynamic drag and lessen the aerodynamic
effectiveness of the control surface due to "leakage" at the end
portions of the control device.
It is therefore evident that there exists a need in the art for an
improved control device system which has a mitigated torque power
requirement and mitigates the formation of gaps and abrupt surface
contour changes occurring between an aerodynamic lifting surface
and an attached control device.
SUMMARY OF THE INVENTION
In accordance with the present invention, there is provided an
aerodynamic control device for use with an aerodynamic lifting
member. The lifting member is defined by a horizontal reference
plane disposed therethrough. The control device is provided with at
least one support rotor extending from the lifting member. The
support rotor is sized and configured to rotate about a rotor axis
of rotation which is disposed generally parallel to the horizontal
reference plane. The support rotor has an inboard segment which is
disposed along the rotor axis of rotation and in rotational
communication with the lifting member. The support rotor has an
outboard segment disposed off-set from the rotor axis of rotation.
The control device is further provided with a control device body
which is engaged with the outboard segment of the support rotor.
The control device body is sized and configured to translate
generally orthogonal to the horizontal reference plane in response
to rotation of the support rotor. Preferably, the control device
body has a body trailing edge and axis of rotation of the support
rotor is disposed generally perpendicular to the body trailing
edge.
In the preferred embodiment of the present invention, rotational
actuators are provided for rotating the support rotors. The
actuators are disposable within the lifting member and in
mechanical communication with the inboard segments of the support
rotors. Further, the at least one support rotor comprises a pair of
support rotors. The control device body has a slot formed therein.
The outboard segments of the support rotors are sized and
configured to slidably engage the slot. Opposing rotation of the
support rotors causes the control device body to translate
orthogonal to the horizontal reference plane. Further, the control
device body is sized and configured to rotate about a roll axis
which is generally parallel to the rotor axes of rotation in
response to a differential amount of rotation of the support
rotors.
Preferably, the aerodynamic lifting member has an indenture formed
therein. The indenture is defined by first and second shoulder
portions. The control device body has opposing first and second
ends thereof. The control device further comprises first and second
transition portions respectively attached to the first and second
ends of the control device body. The first and second transition
portions are attached to the first and second shoulder portions of
the indenture. The first and second transition portions are sized
and configured to deform in response to translation of the control
device body.
In addition, the lifting member has upper and lower lifting member
surfaces and the control device body has upper and lower body
surfaces. The control device is further provided with upper and
lower flexible outer skins. The upper flexible outer skin is
attached to the upper lifting member surface and the upper body
surface and the lower flexible outer skin is attached to the lower
lifting member surface and the lower body surface. The outer skins
are sized and configured to deform in response to translation of
the control device body. In particular, the control device body has
an upper deflected position with the control device body translated
in a direction of the upper body surface. Similarly, the control
device body has a lower deflected position with the control device
body translated in a direction of the lower body surface. The upper
and lower flexible outer skins are sized and configured to be
disposed in tension while the control device body is in either the
upper or lower deflected positions.
As such, based on the foregoing, the present invention mitigates
the inefficiencies and limitations associated with prior art
aerodynamic control devices. Significantly, actuation of the
control device of the present invention is effectuated by the
application of torque to the support rotor for translating the
control device body generally orthogonal (i.e., vertically) to the
horizontal reference plane of the lifting member. As further
discussed below, such a configuration is particularly advantageous
because the power or torque requirement of the control device is
different than that of conventional prior art rotating control
devices.
In general, as the deflection of a control device is increased,
there is a corresponding increase in control surface area which is
projected upon a fuselage station plane or that plane which is
generally orthogonal to the direction of flight. As one of ordinary
skill in the art can appreciate, as such projected control surface
area is increased, there is a corresponding increase in the induced
air load against the control device.
A conventional trailing edge control device, such as a flap, is
configured to rotate about a spanwise or lateral axis with respect
to the wing or trailing edge thereof. The torque or power
requirement to actuate such a conventional control device is
roughly proportional to the air load against the control device. In
this respect, the torque or power requirement to actuate and
maintain such a conventional control device in a slightly deflected
position is minimal, because the projected surface area and
therefore the air load thereon is minimal. Further, where the
control device is in a maximum deflection position (i.e., flap
fully up or flap fully down), the control device is at its maximum
torque or power actuation requirement.
As mentioned above, actuation of the control device of the present
invention is effectuated by the application of torque to the
support rotors generally perpendicular to a spanwise or lateral
axis of the lifting member. Thus, the rotor axes of rotation are
generally perpendicular to the rotational axis of an
above-described conventional flap-type control device. As a
consequence of such a configuration, unlike a conventional control
device, the torque or power requirement to actuate the control
device of the present invention is not directly proportional to the
air loads impinging thereon. This is because where the control
device is in a fully deflected position with the support rotors
rotated approximately 90.degree. from their normal horizontally
aligned position, the support rotors are at a maximal mechanical
advantage with respect to the impinging air loads. In this respect,
air loads impinging upon the control device body are transferred to
the support rotors in a cantilever fashion with the support rotors
experiencing shear and moment loads. As such, torque required to
cause and maintain translation of the control body is minimal. As
such, the present control device has a generally reduced actuation
torque requirement in comparison to a conventional rotating control
device for comparable air load conditions.
In addition, the flexible outer skins which are attached to and
span between the lifting member and the control device body
advantageously mitigates the aerodynamic penalties due to leakage
at control device hinge line gaps, and gaps between the control
device ends and the lifting member, which are typically associated
with some prior art flap-type control devices.
Further, as mentioned above, outer skins are configured to be
disposed in tension while the control device body is its upper and
lower deflected positions. This is feasible because the control
device body is configured to translate, rather than rotating like
flap-type control devices. As such, this arrangement advantageously
allows for the outer skins to be maintained in tension and
therefore undesirable compression or buckling of the outer skins
are avoided. Thus, the translational movement of the control device
body facilitates maintaining a relatively smooth aerodynamic
contour across both the upper and lower flexible outer skins during
the entire range of motion of the control device body.
Accordingly, the present invention represents a significant advance
in the art.
BRIEF DESCRIPTION OF THE DRAWINGS
These, as well as other features of the present invention, will
become more apparent upon reference to the drawings wherein:
FIG. 1 is a top view of an embodiment of the aerodynamic control
device of the present invention as integrated in an aircraft;
FIG. 2 is an enlarged exploded top-rear perspective view of the
control device of the present invention as integrated with the
starboard wing of the aircraft of FIG. 1 as shown with the control
device in a normal undeflected position;
FIG. 3 is a similar enlarged exploded perspective view of the
control device of FIG. 2 as shown with the control device in a
downward deflected position;
FIG. 4 is a similar enlarged exploded perspective view of the
control device of FIG. 2 as shown with the control device in an
upward deflected position;
FIG. 5 is a side view of the control device of FIG. 2 as seen along
axis 5--5;
FIG. 6 is a side view of the control device of FIG. 3 as seen along
axis 6--6;
FIG. 7 is a side view of the control device of FIG. 4 as seen along
axis 7--7;
FIG. 8 is an enlarged exploded top-forward perspective view of the
control device of FIG. 2;
FIG. 9 is an enlarged exploded top-forward perspective view of the
control device of FIG. 3;
FIG. 10 is an enlarged exploded top-forward perspective view of the
control device of FIG. 4;
FIG. 11 is an enlarged exploded top-rear perspective view of the
control device of the another embodiment of the present invention
as integrated with the starboard tail fin of FIG. 1 as shown with
the control device in a normal undeflected position; and
FIG. 12 is a similar enlarged exploded perspective view of the
control device of FIG. 11 as shown with the control device in a
downward deflected position.
DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring now to the drawings wherein the showings are for purposes
of illustrating a preferred embodiment of the present invention
only, and not for purposes of limiting the same, FIGS. 1-12
illustrate an aerodynamic control device which is constructed in
accordance with the present invention. As will be described in more
detail below, the control device may be integrated with an
aerodynamic lifting member for facilitating aerodynamic control of
an aircraft.
Referring now to FIG. 1, there is depicted a representative
aircraft 10 having opposing wings 12. The wings 12 have wing
trailing edges 14. In one embodiment of the present invention, the
wings 12 each have an aerodynamic control device 16 which are
configured to be integrally disposed therewithin at the wing
trailing edges 14. The exemplar aircraft 10 is further provided
with a pair of vertical tails 18. In another embodiment of the
present invention, the vertical tails 18 each have a control device
20 which are configured to be integrally disposed therewithin. It
is contemplated that the present invention may be generally
practiced in conjunction with any number of aerodynamic lifting
members, such as those symbolically depicted in FIG. 1 as wings 12
and vertical tails 18.
For purposes of only describing the present invention and not
limiting the same, however, FIGS. 2-10 symbolically depict an
embodiment of the present invention as integrated with an
aerodynamic lifting member in the form of the starboard wing 12.
Similarly, FIGS. 11-12 symbolically depict another embodiment of
the present invention as integrated with an aerodynamic lifting
member in the form of the starboard vertical tail 18. It is
contemplated that the present invention may be practiced with other
aerodynamic lifting members which are oriented in other angular
orientations and are of various shapes, sizes and
configurations.
Referring now to FIG. 2, for ease of explanation, there is depicted
an enlarged partial view of the starboard wing 12 of FIG. 1 as seen
from a top-rear perspective. The wing 12 is provided with a
indenture 22 adjacent the wing trailing edge 14. The indenture 22
is generally defined by first and second shoulder portions 24, 26
and an inboard wall portion 28 interposed therebetween. While the
first and second shoulder portions 24, 26 and the inboard wall
portion 28 are depicted as being solid surfaces, it is contemplated
that such portions 24, 26, 28 are merely reference boundaries which
define the indenture 22. In this regard, the first and second
shoulder portions 24, 26 and the inboard wall portion 28 may be
built up in a typical airframe construction, with ribs and a
trailing edge spar.
While the first and second shoulder portions 24, 26 are depicted as
being generally aligned chordwise and the inboard wall portion 28
is depicted as being generally aligned parallel with the wing
trailing edge 14, such portions 24, 26, 28 may be configured at
other angular orientations. This would allow for a variable sweep
angle of the control surface or to provide for alignment with other
manufacturing breaks. The first and second shoulder portions 24, 26
will generally intersect sharply with the wing trailing edge 14, as
depicted. Should the wing trailing edge 14 be of a more rounded
configuration, the indenture 22 may be designed to accommodate such
a rounded contour. Furthermore, the indenture may be integrated at
the distal tip of an aircraft wing such that the first shoulder
portion 24 is disposed within a forward facing edge and the second
shoulder portion 26 is disposed within a trailing edge.
The control device 16 is provided with a control device body 30
which is sized and configured to be received by the indenture 22.
The control device 16 is further provided with a pair of support
rotors 32a-b which extend from the indenture 22 for supporting the
control device body 30. Importantly, as discussed in detail below,
the control device body 30 is configured to translate with respect
to the wing 12 from a normal undeflected position as shown in FIG.
2. Correspondingly, FIG. 5 depicts the control device body 30 in a
cross-sectional side view in this normal undeflected position. FIG.
8 depicts the control device body 30 of FIG. 1 as seen from a
top-forward perspective. Similar views are depicted with the
control device body 30 in an downward deflected position in FIGS.
3, 6 and 9. The control device body 30 is depicted in an upward
deflected position in FIGS. 4, 7 and 10.
The control device body 30 has a body trailing edge 34, an opposing
inboard side 36, and opposing first and second ends 38, 40. The
body trailing edge 34 is configured to be aligned with the wing
trailing edge 14 when the control device body 30 is in its
undeflected position, as shown in FIG. 2. The control device body
30 further has upper and lower body surfaces 42, 44 which taper to
the body trailing edge 34.
It is contemplated that as the present invention may be practiced
with other aerodynamic lifting members which are oriented in other
angular orientations and are of various shapes, sizes and
configurations, the control device body 30 may take the form of
other shapes, sizes, orientations and configurations. For example,
although not shown, where the present invention is integrated at
the distal tip of a wing, the control device body 30 may be of a
more corner or L-shape.
The wing 12 is provided with upper and lower wing surfaces 46, 48
which taper to the wing trailing edge 14. The upper and lower wing
surfaces 46, 48 generally define an aerodynamic surface contour 50.
As one of ordinary skill in the art can appreciate, when the
control device body 30, and thus the control device 16, is in an
undeflected position, as shown in FIG. 2, the upper and lower body
surfaces 42, 44 are configured to generally follow the aerodynamic
surface contour 50. In this respect the upper and lower body
surfaces 42, 44 further define the aerodynamic surface contour
50.
As mentioned above, the control device 16 is provided with a pair
of support rotors 32a-b. The support rotors 32a-b are used to
attach the control device body 30 to the wing 12. The support
rotors 32a-b each have inboard and outboard segments 52, 54 which
may be connected by a cross segment 56. Preferably, the
cross-segment 56 is canted at an angle such that the intersection
or elbow between the cross-segment 56 and the inboard and outboard
segments 52, 54 form obtuse angles. Such canting of the
cross-segment 56 advantageously avoids undue vertical extension of
the intersection between the cross-segment 56 and the inboard and
outboard segments 52, 54 when the support rotors 32a-b are rotated.
In the preferred embodiment of the present invention, the inboard
and outboard segments 52, 54 are aligned generally parallel to each
other and are separated by an off-set distance (OS),
Importantly, the support rotors 32a-b facilitate translational
movement of the control device body 30 relative to the wing 12. In
this respects the wing 12 is generally defined by a horizontal
reference plane defined by X and Y axes As such, the support rotors
32a-b facilitates translational movement of the control device body
30 relative to the horizontal reference plane (X-Y). Each of the
support rotors 32a-b are sized and configured to rotate about rotor
axes of rotation Y', Y" disposed generally parallel to the
horizontal reference plane (X-Y) As such, preferably, the rotor
axes of rotation Y', Y" are disposed generally perpendicular to the
body trailing edge 34 when in its undeflected position, as shown in
FIG. 2. The inboard segments 52 are disposed along the rotor axes
of rotation Y', Y" and are in rotational communication with the
wing 12. This arrangement allows the control device body 30 to
translate generally orthogonal to the horizontal reference plane
(X-Y) in response to rotation of the support rotors 32a-b.
The inboard segments 52 are rotatably engaged with the inboard wall
portion 28 of the indenture 22. In particular, the inboard segments
52 are engaged by rotary actuators 58 which are fixed to the wing
12. It is contemplated that the rotary actuators 58 may be chosen
from those which are well known to one of ordinary skill in the
art.
The outboard segments 54 are preferably engaged with the inboard
side 36 of the control device body 30 in slidable and rotatable
communication. In this regard, the control device body 30 is
provided with a slot 60 which is formed in the inboard side 36
thereof. The outboard segments 54 may be fitted with roller
bearings 62, although other methods and apparatus for facilitating
such slidable and rotatable engagement may be chosen from those
which are well known to one of ordinary skill in the art.
It is contemplated that the translational movement of the control
device body 30 is effectuated by rotating the support rotors 32a-b
in opposing rotational directions. Referring to FIGS. 3, 6 and 9,
the support rotors 32a-b are rotated by 90.degree. in opposite
directions relative to their respective positions in FIGS. 2, 5 and
8. As a result of such rotation of the support rotors 32a-b about
the inboard segments 52 thereof, the outboard segments 54 translate
downward away from each other. This downward movement causes the
slidably and rotatably engaged control body 30 to likewise move
downward as shown. As can be seen, the maximal amount of downward
translation of the control body 30 is controlled by the off-set
distance (OS) between the inboard and outboard segments 52, 54.
Similarly, referring now to FIGS. 4, 7 and 10, the support rotors
32a-b may be rotated so as to move the outboard segments 54 upward
and away from each other. This upward movement causes the slidably
and rotatably engaged control body 30 to move upward as well. The
maximal amount of upward translation of the control body 30 is
controlled by the off-set distance (OS) between the inboard and
outboard segments 52, 54 .
The support rotors 32a-b are sized and configured to be of
sufficient mechanical strength to facilitate the transfer of any
air loads (and induced strains in flexible transition sections 64,
66 and a flexible outer skin 68, as discussed below) which take the
form of both shear and bending loads. The particular material
selection for the support rotors 32a-b is chosen from those which
are well known to one of ordinary skill in the art, and may include
a tubular metal alloy. It is contemplated that when the control
device 16 is in a fully deflected position with the support rotors
32a-b rotated approximately 90.degree. from their normal
horizontally aligned position, the support rotors 32a-b are at a
maximal mechanical advantage with respect to any impinging air
loads. In this respect, air loads impinging upon the upper or lower
body surfaces 42, 44 are transferred to the support rotors 32a-b in
a cantilever fashion with the support rotors 32a-b experiencing
shear and moment loads. As such, the air load component of the
torque required to cause and maintain translation of the control
device body 30 is mitigated.
While the support rotors 32a-b are depicted as being rotated by
comparable amounts of angular rotation, differential rotations may
be facilitated. As one of ordinary skill in the art will
appreciate, such differential rotation would result in the control
device body 30 being rotated about an axis of rotation which is
parallel to the rotor axes of rotation Y', Y". This would provided
a means of tailoring the aerodynamic function of the control
surface. For example, considering a trailing edge device, greater
pitch control may be obtained by greater relative deflections of
the inboard most rotor 32. Similarly, greater roll control could be
achieved by greater relative deflection of the outboard most rotor
32. As such, the control device of the present invention may be
adapted to replace more traditional single purpose-type of control
devices.
Preferably, the control device 16 is provided with first and second
transition portions 64, 66. The first transition portion 64
attaches the first end 38 of the control device body 30 to the
first shoulder portion 24 of the indenture 22. The second
transition portion 66 attaches the second end 40 of the control
device body 30 to the second shoulder portion 26 of the indenture
22. Importantly, the first and second transition portions 64, 66
are sized and configured to deform in response to translation of
the control device body 30. As can be seen, the cross sectional
shaping of the transition portions 64, 66 generally conforms to
that of the control device body 30 and follows the aerodynamic
surface contour 50. As such, the transition sections 64, 66 may
blend with the control device body 30 so as to form a unitary
structure. The transition portions 64, 66 are configured to smooth
the discontinuity of the surface contour 50 when the control device
body 30 is deflected. In this respect, the transition portions 64,
66 further define the surface contour 50. As shown in FIGS. 3 and
4, the transition portions 64, 66 are configured to assume an
S-shape in response to the translation of the control device body
30 from its normal undeflected position. It is contemplated that
the transition portions 64, 66 may be configured to more sharply
transition in a ramp-like manner rather than the depicted curved
S-shape. The particular material for the transition sections 64, 66
are chosen from those which are well known to one of ordinary skill
in the art and may include a flexible elastomeric material such as
durable rubber. The methods of attachment of the transition
portions 64, 66 to the control device body 30 and the shoulder
portions 24, 26 are chosen from those which are well known to one
of ordinary skill in the art.
Preferably, the control device 16 is further provided with a
flexible outer skin 68 attached to the wing 12 and the control
device body 30 spanning over the indenture 22. The outer skin 68 is
in mechanical communication with, preferably bonded to, the upper
and lower body surfaces 42, 44 and the upper and lower wing
surfaces 46, 48 adjacent the indenture 22. The shape of the
flexible outer skin 68 is dictated by the position of the
underlying control device body 30 and the transition portions 64,
66. Thus, the outer skin 68 is sized and configured to deform in
response to movement of the control device body 30, and further
defines the aerodynamic surface contour 50. Although the outer skin
68 is depicted as completely wrapping around the control device
body 30, the outer skin 68 does not have to completely cover the
control device body 30. In this regard, the outer skin 68 may be
formed of multiple pieces and attached along the edge of the upper
and lower body surfaces 42, 44. Thus, the outer skin 68 is used to
form a transition surface about the "hingeline" formed between the
control device body 30 and the indenture 22. Further, the outer
skin 68 may include reinforcement rods which are integrated with
the outer skin 68 for supporting air loads thereat. The particular
material selection for the outer skin 68 and method of attachment
are chosen from those which are well known to one of ordinary skill
in the art, and may include, for example, elastomeric materials
such as rubber sheeting.
Referring now to FIGS. 11 and 12, there is depicted another
embodiment of the present invention as integrated with the
starboard vertical tail 18 of FIG. 1. FIG. 11 depicts the control
device 20 in a normal undeflected position and FIG. 12 depicted the
control device 20 in a outboard deflected position. The control
device 20 is provided with a control device body 70 having first
and second ends 72, 74 thereof. The second end 74 is relatively
exposed so as to form a distal tip 78 of the vertical tail 18. The
control device body 70 is joined to the vertical tail 20 via an
inboard transition portion 76 which is constructed and configured
in an analogous manner as the first transition portion 64 of the
above described embodiment. The control device 20 may be further
provided with an outboard transition portion 80 which is attached
to an inboard side 82 of the control device body 70. In this
regard, the outboard transition portion 80 further defines the
distal tip 78. The control device 20 is further provided with
support rotors 84a-b which are constructed and configured in an
analogous manner as the support rotors 32a-b of the above described
embodiment.
Additional modifications and improvements of the present invention
may also be apparent to those of ordinary skill in the art. Thus,
the particular combination of parts described and illustrated
herein is intended to represent only one embodiment of the present
invention, and is not intended to serve as limitations of
alternative devices within the spirit and scope of the
invention.
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